Weapon interface system and delivery platform employing the same

ABSTRACT

A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto.

This application is a continuation of U.S. patent application Ser. No.15/412,118 entitled “Weapon Interface System and Delivery PlatformEmploying the Same,” filed Jan. 23, 2017, issued on Jul. 24, 2018 asU.S. patent Ser. No. 10/029,791, which is a continuation of U.S. patentapplication Ser. No. 13/975,609 entitled “Weapon Interface System andDelivery Platform Employing the Same,” filed Aug. 26, 2013, issued onJan. 24, 2017 as U.S. Pat. No. 9,550,568, which is a continuation ofU.S. patent application Ser. No. 13/399,873 entitled “Weapon InterfaceSystem and Delivery Platform Employing the Same,” filed Feb. 17, 2012,issued on Aug. 27, 2013 as U.S. Pat. No. 8,516,938, which is adivisional of U.S. patent application Ser. No. 11/925,471 entitled“Weapon Interface System and Delivery Platform Employing the Same,”filed Oct. 26, 2007, issued on Feb. 21, 2012 as U.S. Pat. No. 8,117,955,which claims the benefit of U.S. Provisional Application No. 60/855,084entitled “Weapon System, and Weapon Enhancements for Increased MissionEffectiveness and Decreased Mission Time Lines,” filed Oct. 26, 2006,which applications are incorporated herein by reference.

TECHNICAL FIELD

The present invention is directed, in general, to weapon systems and,more specifically, to a weapon interface system, and method of operatingthe same.

BACKGROUND

Present rules of engagement demand that precision guided weapons andweapon systems are necessary. According to well-documented reports,precision guided weapons have made up about 53 percent of all strikeweapons employed by the United States from 1995 to 2003. The trendtoward the use of precision weapons will continue. Additionally, strikeweapons are used throughout a campaign, and in larger numbers than anyother class of weapons. This trend will be even more pronounced asunmanned airborne vehicles (“UAVs”) take on attack roles.

Each weapon carried on a launch platform (e.g., aircraft, ship,artillery) must be tested for safety, compatibility, and effectiveness.In some cases, these qualification tests can cost more to perform thanthe costs of the development of the weapon system. As a result,designers often choose to be constrained by earlier qualifications. Inthe case of smart weapons, this qualification includes datacompatibility efforts. Examples of this philosophy can be found in theair to ground munitions (“AGM”)-154 joint standoff weapon (“JSOW”),which was integrated with a number of launch platforms. In the process,a set of interfaces were developed, and a number of other systems havesince been integrated which used the data sets and precedents developedby the AGM-154. Such qualifications can be very complex.

An additional example is the bomb live unit (“BLU”)-116, which isessentially identical to the BLU-109 warhead in terms of weight, centerof gravity and external dimensions. However, the BLU-116 has an external“shroud” of light metal (presumably aluminum alloy or something similar)and a core of hard, heavy metal. Thus, the BLU-109 was employed toreduce qualification costs of the BLU-116.

Another means used to minimize the time and expense of weaponsintegration is to minimize the changes to launch platform software. Asweapons have become more complex, this has proven to be difficult. As aresult, the delay in operational deployment of new weapons has beenmeasured in years, often due solely to the problem of aircraft softwareintegration.

Some weapons such as the Paveway II laser guided bomb [also known as theguided bomb unit (“GBU”)-12] have no data or power interface to thelaunch platform. Clearly, it is highly desirable to minimize this formof interface and to, therefore, minimize the cost and time needed toachieve military utility.

Another general issue to consider is that low cost weapons are bestdesigned with modularity in mind. This generally means that changes canbe made to an element of the total weapon system, while retaining manyexisting features, again with cost and time in mind.

Another consideration is the matter of avoiding unintended damage, suchas damage to non-combatants. Such damage can take many forms, includingdirect damage from an exploding weapon, or indirect damage. Indirectdamage can be caused by a “dud” weapon going off hours or weeks after anattack, or if an enemy uses the weapon as an improvised explosivedevice. The damage may be inflicted on civilians or on friendly forces.

One term of reference is “danger close,” which is the term included inthe method of engagement segment of a call for fire that indicates thatfriendly forces or non-combatants are within close proximity of thetarget. The close proximity distance is determined by the weapon andmunition fired. In recent United States engagements, insurgent forcesfighting from urban positions have been difficult to attack due to suchconsiderations.

To avoid such damage, a number of data elements may be provided to theweapon before launch, examples of such data include information aboutcoding on a laser designator, so the weapon will home in on the rightsignal. Another example is global positioning system (“GPS”) informationabout where the weapon should go, or areas that must be avoided. Otherexamples could be cited, and are familiar to those skilled in the art.

Therefore, what is needed is a small smart weapon that can be accuratelyguided to an intended target with the effect of destroying that targetwith little or no collateral damage of other nearby locations. Also,what is needed is such a weapon having many of the characteristics ofprior weapons already qualified in order to substantially reduce thecost and time for effective deployment. Also, what is needed is a weaponthat does not require the use of mechanical connectors or lanyards forproper operation.

SUMMARY OF THE INVENTION

These and other problems are generally solved or circumvented, andtechnical advantages are generally achieved, by advantageous embodimentsof the present invention, which includes a weapon interface system, andmethods of operating the same. In one embodiment, the weapon interfacesystem is coupled to an electrical interconnection system of a deliveryplatform and a weapon system coupled to a rack system. The weaponinterface system includes a translation interface configured to providean interface between the electrical interconnection system and aninductive power and data circuit. The weapon interface system alsoincludes a weapon coupler, coupled to the translation interface,configured to provide an inductive coupling to the weapon system toprovide mission information thereto.

The foregoing has outlined rather broadly the features and technicaladvantages of the present invention in order that the detaileddescription of the invention that follows may be better understood.Additional features and advantages of the invention will be describedhereinafter which form the subject of the claims of the invention. Itshould be appreciated by those skilled in the art that the conceptionand specific embodiment disclosed may be readily utilized as a basis formodifying or designing other structures or processes for carrying outthe same purposes of the present invention. It should also be realizedby those skilled in the art that such equivalent constructions do notdepart from the spirit and scope of the invention as set forth in theappended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

For a more complete understanding of the present invention, and theadvantages thereof, reference is now made to the following descriptionstaken in conjunction with the accompanying drawings, in which:

FIG. 1 illustrates a view of an embodiment of a weapon system inaccordance with the principles of the present invention;

FIG. 2 illustrates a diagram demonstrating a region including a targetzone for a weapon system in accordance with the principles of thepresent invention;

FIG. 3 illustrates a perspective view of an embodiment of a weaponconstructed according to the principles of the present invention;

FIG. 4 illustrates a diagram demonstrating a region including a targetzone for a weapon system in accordance with the principles of thepresent invention;

FIG. 5 illustrates a diagram of an embodiment of a folding lug switchassembly constructed in accordance with the principles of the presentinvention;

FIGS. 6A and 6B illustrate diagrams demonstrating a four quadrant semiactive laser detector constructed in accordance with the principles ofthe present invention;

FIGS. 7A and 7B illustrate the properties of a conventional and fastfresnel lens (“FFL”) constructed in accordance with the principles ofthe present invention;

FIG. 8 illustrates a diagram of an embodiment of a pseudorandom patternfor a FFL constructed in accordance with the principles of the presentinvention;

FIGS. 9A and 9B illustrate views of an embodiment of hybrid opticsemployable with a guidance section of a weapon constructed in accordancewith the principles of the present invention;

FIG. 10 illustrates a view of an embodiment of an aft sectionconstructed in accordance with the principles of the present invention;

FIG. 11 illustrates a view of an embodiment of an aft sectionconstructed in accordance with the principles of the present invention;

FIGS. 12A and 12B illustrate views of an embodiment of a variable aspectwing ratio for the tail fins of an aft section constructed in accordancewith the principles of the present invention;

FIGS. 13A to 13F illustrate views of an embodiment of a variable aspectwing ratio for the tail fins of an aft section constructed in accordancewith the principles of the present invention;

FIGS. 14A to 14D illustrate views of another embodiment of a weaponincluding the tail fins of an aft section thereof constructed inaccordance with the principles of the present invention;

FIG. 15 illustrates a diagram of an exemplary inductive power and datainterface;

FIG. 16 illustrates a diagram of a representation of the MIL-STD-1553;

FIGS. 17, 18A and 18B illustrate diagrams of exemplary interfacescontrolled by a MIL-STD-1760;

FIGS. 19 and 20 illustrate diagrams of exemplary triple ejector racks;

FIG. 21 illustrates a block diagram of an embodiment of a deliveryplatform constructed according to the principles of the presentinvention;

FIG. 22 illustrates a view of an embodiment of a rack system andportions of a weapon interface system constructed according to theprinciples of the present invention;

FIG. 23 illustrates a diagram of an embodiment of a weapon couplerconstructed according to the principles of the present invention;

FIG. 24 illustrates a view of an embodiment of a rack system andportions of a weapon interface system constructed according to theprinciples of the present invention; and

FIGS. 25 to 28B illustrate cross sectional views of embodiments ofweapon couplers constructed according to the principles of the presentinvention.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

The making and using of the presently preferred embodiments arediscussed in detail below. It should be appreciated, however, that thepresent invention provides many applicable inventive concepts that canbe embodied in a wide variety of specific contexts. The specificembodiments discussed are merely illustrative of specific ways to makeand use the invention, and do not limit the scope of the invention.

It should be understood that the military utility of the weapon can onlybe fully estimated in the context of a so-called system of systems,which includes a guidance section or system, the delivery vehicle orlaunch platform, and other things, in addition to the weapon per se. Inthis sense, a weapon system is disclosed herein, even when we aredescribing a weapon per se. One example is seen in the discussion of theGBU-12, wherein design choices within the weapon were reflected in thedesign and operation of many aircraft that followed the introduction ofthe GBU-12. Another example is the use of a laser designator for laserguided weapons. Design choices in the weapon can enhance or limit theutility of the designator. Other examples can be cited. Those skilled inthe art will understand that the discussion of the weapon per seinherently involves a discussion of the larger weapon system of systems.Therefore, improvements within the weapon often result in correspondingchanges or improvements outside the weapon, and new teachings aboutweapons teach about weapon platforms, and other system of systemselements.

In accordance therewith, a class of warhead assemblies, constitutingsystems, methods, and devices, with many features, including multiple,modular guidance subsystems, avoidance of collateral damage, unexplodedordinance, and undesirable munitions sensitivity is described herein. Inan exemplary embodiment, the warheads are Mark derived (e.g., MK-76) orbomb dummy unit (“BDU”) derived (e.g., BDU-33) warheads. The MK-76 isabout four inches in diameter, 24.5 inches in length, 95-100 cubicinches (“cu”) in internal volume, 25 pounds (“lbs”) and accommodates a0.85 inch diameter practice bomb cartridge. This class of assemblies isalso compatible with existing weapon envelopes of size, shape, weight,center of gravity, moment of inertia, and structural strength to avoidlengthy and expensive qualification for use with manned and unmannedplatforms such as ships, helicopters, self-propelled artillery and fixedwing aircraft, thus constituting systems and methods for introducing newweapon system capabilities more quickly and at less expense. Inaddition, the weapon system greatly increases the number of targets thatcan be attacked by a single platform, whether manned or unmanned.

In an exemplary embodiment, the general system envisioned is based onexisting shapes, such as the MK-76, BDU-43, or laser guided traininground (“LGTR”). The resulting system can be modified by the addition orremoval of various features, such as global positioning system (“GPS”)guidance, and warhead features. In addition, non-explosive warheads,such as those described in U.S. patent application Ser. No. 10/841,192entitled “Weapon and Weapon System Employing The Same,” to Roemerman, etal., filed May 7, 2004, and U.S. patent application Ser. No. 10/997,617,entitled “Weapon and Weapon System Employing the Same,” to Tepera, etal., filed Nov. 24, 2004, now U.S. Pat. No. 7,530,315, which areincorporated herein by reference, may also be employed with the weaponaccording to the principles of the present invention. Additionally, arelated weapon and weapon system is provided in U.S. patent applicationSer. No. 11/706,489, entitled “Small Smart Weapon and Weapon SystemEmploying the Same,” filed Feb. 15, 2007, now U.S. Pat. No. 7,895,946,which is a continuation-in-part of U.S. patent application Ser. No.11/541,207, entitled “Small Smart Weapon and Weapon System Employing theSame,” filed Sep. 29, 2006, now U.S. Pat. No. 7,690,304, which areincorporated herein by reference.

Another feature of the system is the use of system elements for multiplepurposes. For example, the central structural element of the MK-76embodiment includes an optics design with a primary optical element,which is formed in the mechanical structure rather than as a separatecomponent. Another example is the use of an antenna for both radioguidance purposes, such as GPS, and for handoff communication by meanssuch as those typical of a radio frequency identification (“RFID”)system. For examples of RFID related systems, see U.S. PatentApplication Publication No. 2007/0035383, entitled “Radio FrequencyIdentification Interrogation Systems and Methods of Operating the Same,”to Roemerman, et al., filed Aug. 9, 2006, U.S. Pat. No. 7,019,650entitled “Interrogator and Interrogation System Employing the Same,” toVolpi, et al., issued on Mar. 28, 2006, U.S. Patent ApplicationPublication No. 2006/0077036, entitled “Interrogation System EmployingPrior Knowledge About An Object To Discern An Identity Thereof,” toRoemerman, et al., filed Sep. 29, 2005, U.S. Patent ApplicationPublication No. 2006/0017545, entitled “Radio Frequency IdentificationInterrogation Systems and Methods of Operating the Same,” to Volpi, etal., filed Mar. 25, 2005, U.S. Patent Application Publication No.2005/0201450, entitled “Interrogator And Interrogation System EmployingThe Same,” to Volpi, et al., filed Mar. 3, 2005, all of which areincorporated herein by reference.

Referring now to FIG. 1, illustrated is a view of an embodiment of aweapon system in accordance with the principles of the presentinvention. The weapon system includes a delivery platform such as adelivery vehicle (e.g., an airplane such as an F-14) 110 and at leastone weapon. As demonstrated, a first weapon 120 is attached to thedelivery vehicle (e.g., a wing station) and a second weapon 130 isdeployed from the delivery vehicle 110 intended for a target. Of course,the first weapon 120 may be attached to a rack in the delivery vehicleor a bomb bay therein.

The weapon system is configured to provide energy as derived, withoutlimitation, from a velocity and altitude of the delivery vehicle 110 inthe form of kinetic energy (“KE”) and potential energy to the first andsecond weapons 120, 130 and, ultimately, the warhead and destructiveelements therein. The first and second weapons 120, 130 when releasedfrom the delivery vehicle 110 provide guided motion for the warhead tothe target. The energy transferred from the delivery vehicle 110 as wellas any additional energy acquired through the first and second weapons120, 130 through propulsion, gravity or other parameters, provides thekinetic energy to the warhead to perform the intended mission. While thefirst and second weapons 120, 130 described with respect to FIG. 1represent precision guided weapons, those skilled in the art understandthat the principles of the present invention also apply to other typesof weapons including weapons that are not guided by guidance technologyor systems.

In general, it should be understood that other delivery vehiclesincluding other aircraft may be employed such that the weapons containsignificant energy represented as kinetic energy plus potential energy.As mentioned above, the kinetic energy is equal to “½ mv²,” and thepotential energy is equal to “mgh” where “m” is the mass of the weapon,“g” is gravitational acceleration equal to 9.8 M/sec², and “h” is theheight of the weapon at its highest point with respect to the height ofthe target. Thus, at the time of impact, the energy of the weapon iskinetic energy, which is directed into and towards the destruction ofthe target with little to no collateral damage of surroundings.Additionally, the collateral damage may be further reduced if thewarhead is void of an explosive charge.

Turning now to FIG. 2, illustrated is a diagram demonstrating a regionincluding a target zone for a weapon system in accordance with theprinciples of the present invention. The entire region is about 200meters (e.g., about 2.5 city blocks) and the structures that are nottargets take up a significant portion of the region. For instance, theweapon system would not want to target the hospital and a radiusincluding about a 100 meters thereabout. In other words, the structuresthat are not targets are danger close to the targets. A barracks andlogistics structure with the rail line form the targets in theillustrated embodiment.

Turning now to FIG. 3, illustrated is a perspective view of anembodiment of a weapon constructed according to the principles of thepresent invention. The weapon includes a guidance section 310 includinga target sensor (e.g., a laser seeker) 320, and guidance and controlelectronics and logic to guide the weapon to a target. The target sensor320 may include components and subsystems such as a crush switch, asemi-active laser based terminal seeker (“SAL”) quad detector, a netcast corrector and lenses for an optical system. In accordance with SALsystems, net cast optics are suitable, since the spot for the terminalseeker is normally defocused.

The guidance section 310 may include components and subsystems such as aGPS, an antenna such as a ring antenna 330 (e.g., dual use handoff anddata and mission insertion similar to radio frequency identification andpotentially also including responses from the weapon via similar means),a multiple axis microelectomechanical gyroscope, safety and armingdevices, fuzing components, a quad detector, a communication interface[e.g., digital subscriber line (“DSL”)], and provide features such aslow power warming for fast acquisition and inductive handoff with apersonal information manager. In the illustrated embodiment, the antenna330 is about a surface of the weapon. Thus, the antenna is configured toreceive mission information such as location, laser codes, GPSephemerides and the like before launching from a delivery vehicle toguide the weapon to a target. The antenna is also configured to receiveinstructions after launching from the delivery vehicle to guide theweapon to the target. The weapon system, therefore, includes acommunication system, typically within the delivery vehicle, tocommunicate with the weapon, and to achieve other goals and ends in thecontext of weapon system operation. It should be understood that theguidance section 310 contemplates, without limitation, laser guided, GPSguided, and dual mode laser and GPS guided systems. It should beunderstood that this antenna may be configured to receive various kindsof electromagnetic energy, just as there are many types of RFID tagsthat are configured to receive various kinds of electromagnetic energy.

The weapon also includes a warhead 340 (e.g., a unitary configuration)having destructive elements (formed from explosive or non-explosivematerials), mechanisms and elements to articulate aerodynamic surfaces.A folding lug switch assembly 350, safety pin 360 and cavity 370 arealso coupled to the guidance section 310 and the warhead 340. Theguidance section 310 is in front of the warhead 340. The folding lugswitch assembly 350 projects from a surface of the weapon. The weaponstill further includes an aft section 380 behind the warhead 340including system power elements, a ballast, actuators, flight controlelements, and tail fins 390.

For instances when the target sensor is a laser seeker, the laser seekerdetects the reflected energy from a selected target which is beingilluminated by a laser. The laser seeker provides signals so as to drivethe control surfaces in a manner such that the weapon is directed to thetarget. The tail fins 390 provide both stability and lift to the weapon.Modern precision guided weapons can be precisely guided to a specifictarget so that considerable explosive energy is often not needed todestroy an intended target. In many instances, kinetic energy discussedherein may be sufficient to destroy a target, especially when the weaponcan be directed with sufficient accuracy to strike a specific designatedtarget.

The destructive elements of the warhead 340 may be constructed ofnon-explosive materials and selected to achieve penetration,fragmentation, or incendiary effects. The destructive elements (e.g.,shot) may include an incendiary material such as a pyrophoric material(e.g., zirconium) therein. The term “shot” generally refers a solid orhollow spherical, cubic, or other suitably shaped element constructed ofexplosive or non-explosive materials, without the aerodynamiccharacteristics generally associated with, for instance, a “dart.” Theshot may include an incendiary material such as a pyrophoric material(e.g., zirconium) therein. Inasmuch as the destructive elements of thewarhead are a significant part of the weapon, the placement of thesedestructive elements, in order to achieve the overall weight and centerof gravity desired, is an important element in the design of the weapon.

The non-explosive materials applied herein are substantially inert inenvironments that are normal and under benign conditions. Nominallystressing environments such as experienced in normal handling aregenerally insufficient to cause the selected materials (e.g., tungsten,hardened steel, zirconium, copper, depleted uranium and other likematerials) to become destructive in an explosive or incendiary manner.The latent lethal explosive factor is minimal or non-existent. Reactiveconditions are predicated on the application of high kinetic energytransfer, a predominantly physical reaction, and not on explosiveeffects, a predominantly chemical reaction.

The folding lug switch assembly 350 is typically spring-loaded to folddown upon release from, without limitation, a rack on an aircraft. Thefolding lug switch assembly 350 permits initialization after launch (noneed to fire thermal batteries or use other power until the bomb isaway) and provides a positive signal for a fuze. The folding lug switchassembly 350 is consistent with the laser guided bomb (“LGB”) strategyusing lanyards, but without the logistics issues of lanyards. Thefolding lug switch assembly 350 also makes an aircraft data and powerinterface optional and supports a visible “remove before flight” pin.The folding lug switch assembly 350 provides a mechanism to attach theweapon to a delivery vehicle and is configured to close after launchingfrom the delivery vehicle thereby satisfying a criterion to arm thewarhead. It should be understood, however, that the folding lug switchassembly 350, which is highly desirable in some circumstances, can bereplaced with other means of carriage and suspension, and is only one ofmany features of the present invention, which can be applied indifferent combinations to achieve the benefits of the weapon system.

Typically, the safety pin 360 is removed from the folding lug switchassembly 350 and the folding lug switch assembly 350 is attached to arack of an aircraft to hold the folding lug switch assembly 350 in anopen position prior to launch. Thus, the safety pin 360 provides amechanism to arm the weapon. Once the weapon is launched from theaircraft, the folding lug switch assembly 350 folds down into the cavity370 and provides another mechanism to arm the weapon. A delay circuitbetween the folding lug switch assembly 350 and the fuze may be yetanother mechanism to arm or provide time to disable the weapon afterlaunch. Therefore, there are often three mechanisms that are satisfiedbefore the weapon is ultimately armed enroute to the target.

A number of circuits are now well understood that use power from radiofrequency or inductive fields to power a receiving chip and store data.The antenna includes an interface to terminate with the aircraftinterface at the rack for loading relevant mission information includingtarget, location, laser codes, GPS ephemerides and the like before beinglaunched. Programming may be accomplished by a hand-held device similarto a fuze setter or can be programmed by a lower power interface betweena rack and the weapon. Other embodiments are clearly possible to thoseskilled in the art. The antenna serves a dual purpose for handoff andGPS. In other words, the antenna is configured to receive instructionsafter launching from the delivery vehicle to guide the weapon to thetarget. Typically, power to the weapon is not required prior to launch,therefore no umbilical cable is needed. Alternative embodiments forpower to GPS prior to launch are also contemplated herein.

The modular design of the weapon allows the introduction of featuressuch as GPS and other sensors as well. Also, the use of a modularwarhead 340 with heavy metal ballast makes the low cost kinetic [no highexplosives (“HE”)] design option practical and affordable.

As illustrated in an exemplary embodiment of a weapon in the TABLE 1below, the weapon may be designed to have a similar envelope, mass, andcenter of gravity already present in existing aircraft for a practicebomb version thereof. Alternatively, the weapon may be designed withother envelopes, masses, and centers of gravity, as may be availablewith other configurations, as also being included within the constructsof this invention.

TABLE 1 DENSITY (LB/CU WEIGHT VOLUME FUNCTION MATERIAL IN) (LB) (CU IN)Ballast/KE Tungsten 0.695 20.329 29.250 Structure, Metal Aluminum 0.0900.270 3.000 Augmented Charge (“MAC”) Explosive Dome Pyrex 0.074 0.1672.250 Structure Steel 0.260 1.430 5.500 Guidance Misc Electronics 0.0330.800 24.000 Primary Polymer Bonded 0.057 2.040 36.000 ExplosiveExplosive (“PBX”) Total SSW 0.250 25.036 100.000 MK-76 0.250 25.000100.000

In the above example, the weapon is MK-76 derived, but others such asBDU-33 are well within the broad scope of the present invention. Theweapon provides for very low cost of aircraft integration. The warhead340 is large enough for useful warheads and small enough for very highcarriage density. The modular design of the weapon allows many variantsand is compatible with existing handling and loading methods.

The following TABLEs 2 and 3 provide a comparison of several weapons toaccentuate the advantages of small smart weapons such as the MK-76 andBDU-33.

TABLE 2 AIRCRAFT (“A/C”) WEIGHT DIAMETER CANDIDATE CLEARED (LB)(IN-APPROX) REMARKS LGB/MK-81 None 250+ 10 Canceled variant MK-76/BDU33All 25 4 Low drag practice bomb BDU-48 All 10 3.9 High drag practicebomb MK-106 All  5 3.9 High drag practice bomb SDB Most US 285  7.5GBU-39 Small Dia. Bomb

TABLE 3 LARGE CLEARED ENOUGH VIABLE HIGH ON MANY FOR FOR DENSITYCOMPATIBLE WITH CANDIDATE A/C? WARHEAD? EXPORT? CARRIAGE? TUBE LAUNCH?LGB/MK-81 No Yes Yes No No MK-76/ All Yes Yes Yes Yes BDU33 BDU-48 AllNo Yes Yes Yes MK-106 All No Yes Yes Yes SDB Most US Yes No Yes No

The aforementioned tables provide a snapshot of the advantagesassociated with small smart weapons, such as, procurements areinevitable, and the current weapons have limited utility due topolitical, tactical, and legal considerations. Additionally, thetechnology is ready with much of it being commercial off-the-shelftechnology and the trends reflect these changes. The smart weapons arenow core doctrine and contractors can expect production in very largenumbers. Compared to existing systems, small smart weapons exhibitsmaller size, lower cost, equally high or better accuracy, short time tomarket, and ease of integration with an airframe, which are key elementsdirectly addressed by the weapon disclosed herein. As an example, thesmall smart weapon could increase an unmanned combat air vehicle(“UCAV”) weapon count by a factor of two or more over a small diameterbomb (“SDB”) such as a GBU-39/B.

The small smart weapons also address concerns with submunitions, whichare claimed by some nations to fall under the land mine treaty. Thesubmunitions are a major source of unexploded ordnance, causingsignificant limitations to force maneuvers, and casualties to civiliansand blue forces. Submunitions are currently the only practical way toattack area targets, such as staging areas, barracks complexes, freightyards, etc. Unexploded ordnance from larger warheads are a primarysource of explosives for improvised explosive devices. While the broadscope of the present invention is not so limited, small smart weaponsincluding small warheads, individually targeted, alleviate or greatlyreduce these concerns.

Turning now to FIG. 4, illustrated is a diagram demonstrating a regionincluding a target zone for a weapon system in accordance with theprinciples of the present invention. Analogous to the regionsillustrated with respect to FIG. 2, the entire region is about 200meters (e.g., about 2.5 city blocks) and the structures that are nottargets take up a significant portion of the region. In the illustratedembodiment, the lethal diameter for the weapon is about 10 meters andthe danger close diameter is about 50 meters. Thus, when the weaponstrikes the barracks, rail line or logistics structure as shown, theweapon according to the principles of the present invention provideslittle or no collateral damage to, for instance, the hospital. Whileonly a few strikes of a weapon are illustrated herein, it may bepreferable to cause many strikes at the intended targets, while at thesame time being cognizant of the collateral damage.

In an exemplary embodiment, a sensor of the weapon detects a target inaccordance with, for instance, pre-programmed knowledge-based data sets,target information, weapon information, warhead characteristics, safeand arm events, fuzing logic and environmental information. In thetarget region, sensors and devices detect the target and non-targetlocations and positions. Command signals including data, instructions,and information contained in the weapon (e.g., a control section) arepassed to the warhead. The data, instructions, and information containthat knowledge which incorporates the functional mode of the warheadsuch as safe and arming conditions, fuzing logic, deployment mode andfunctioning requirements.

The set of information as described above is passed to, for instance, anevent sequencer of the warhead. In accordance therewith, the warheadcharacteristics, safe and arm events, fuzing logic, and deployment modesare established and executed therewith. At an instant that allconditions are properly satisfied (e.g., a folding lug switch assemblyis closed), the event sequencer passes the proper signals to initiate afire signal to fuzes for the warhead. In accordance herewith, afunctional mode for the warhead is provided including rangecharacteristics and the like. Thereafter, the warhead is guided to thetarget employing the guidance section employing, without limitation, anantenna and global positioning system.

Thus, a class of warhead assemblies, constituting systems, methods, anddevices, with many features, including multiple, modular guidancesubsystems, avoidance of collateral damage, unexploded ordinance, andundesirable munitions sensitivity has been described herein. The weaponaccording to the principles of the present invention provides a class ofwarheads that are compatible with existing weapon envelopes of size,shape, weight, center of gravity, moment of inertia, and structuralstrength, to avoid lengthy and expensive qualification for use withmanned and unmanned platforms such as ships, helicopters, self-propelledartillery and fixed wing aircraft, thus constituting systems and methodsfor introducing new weapon system capabilities more quickly and at lessexpense. In addition, the weapon system greatly increases the number oftargets that can be attacked by a single platform, whether manned orunmanned.

Turning now to FIG. 5, illustrated is a diagram of an embodiment of afolding lug switch assembly constructed in accordance with theprinciples of the present invention. More specifically, a folding lug ofthe folding lug switch assembly is shown in an upright position 505 andin a folded position 510. The folding lug switch assembly includes arack and pinion 515, which in an alternative embodiment can also be acam. The folding lug switch assembly also includes a return spring 520that provides the energy to fold the folding lug down and retract aretracting cam 525, which interacts with a switch sear 530 to release anarming pin 535 and thus activate an arming rotor 540, an arming plunger545, and finally a power switch 550. This invention comprehends afolding lug switch assembly that may have multiple functions beyondarming including weapon guidance. It may also have multiple poles andmultiple throws that, as an example, may be used for purposes such asisolating arming circuits from other circuits.

Referring once more to the target sensor discussed above, a semi-activelaser (“SAL”) seeker is typically the most complex item in SAL guidedsystems, and SAL is the most commonly used means of guiding precisionweapons. Therefore, a low cost and compact approach, consistent with avery confined space, is highly desirable.

Turning now to FIGS. 6A and 6B, illustrated are diagrams demonstrating afour quadrant semi active laser detector constructed in accordance withthe principles of the present invention. More specifically, FIG. 6Arepresents a typical four quadrant seeker having quadrants A, B, C, andD. This system is capable of providing both elevation information (“EL”)and azimuth information (“AZ”) according to the following equations:

EL=((A+B)−(C+D))/(A+B+C+D), and

AZ=((A+D)−(B+C))/(A+B+C+D).

A reflected spot from a laser 605 is shown in quadrant B where the spotis focused on the plane of the active detecting area.

Turning now to FIG. 6B, illustrated is the same basic conditions of FIG.6A, except that a spot 610 has been intentionally defocused so that, fora target near bore sight, a linear (i.e., proportional) output results.By these illustrations, it is therefore seen that focused systems areprone to indicate in which quadrant a signal may reside, while adefocused system will support proportional guidance as shown byilluminating more than one quadrant in the region of boresight whereproportional guidance is most important.

Turning now to FIGS. 7A and 7B, illustrated are the properties of aconventional and fast fresnel lens (“FFL”) constructed in accordancewith the principles of the present invention. More specifically, FIG. 7Aillustrates an embodiment of the focusing element of a SAL employing aconventional convex lens. The small volumes require fast optics whichare usually expensive. Also, linear outputs are hard to achieve withfast optics or low cost, and nearly impossible with both. Point 710illustrates a correct focus point and point 705 illustrates error in thelens' focusing ability. For reasonable angles, this error is often quitesmall.

Turning now to FIG. 7B, illustrated is an illustration of an embodimentof the present invention employing a FFL. A fresnel lens is a type oflens invented by Augustin-Jean Fresnel and originally developed forlighthouses, as the design enables the construction of lenses of largeaperture and short focal length without the weight and volume ofmaterial which would be required in conventional lens design. Comparedto earlier lenses, the fresnel lens is much thinner, thus passing morelight. Note that it is often constructed with separate concentricridges. This innovative approach provides reductions in weight, volume,and cost. A point 720 illustrates a correct focus, wherein a point 715illustrates an error in the FFL's ability to provide a correct focus.Though this lens is smaller and lighter, the error in correct focus,even for small angles off boresight is not insignificant.

An alternative embodiment that specifically addresses the focus errorsdiscussed above for a FFL is to add lens stopping (i.e., opticalbarriers) in those regions where unwanted energy is most likely tooriginate. This slightly reduces the amount of light passed on by thelens, but also significantly reduces the focusing error for a net gainin performance.

Yet another embodiment of this invention is to replace the concentriccircles of the FFL with randomized circles as illustrated in FIG. 8.Fresnel lens boundaries between surfaces are well known sources of someof the problems illustrated above. Concentric circles 805 are typical ofthis problem. By innovatively using a pseudo-random walk to define theboundaries, instead of concentric circles, the scattering is much morerandom, resulting in a less focused scattering pattern and thereforefocusing errors are less likely to constructively interfere. Thus, thefast fresnel lens is formed from multiple substantially concentriccircles to which is added a pseudo-random walk that results in smalllocal perturbations of a respective substantially concentric circle. Inother words, the fast fresnel lens is formed from multiple substantiallyconcentric circles that include random perturbations 810. Additionally,for lenses that are cast, rather than ground, there is no need for thelens surface boundaries to be circular. Yet another embodiment of thisinvention is to introduce multi-element hybrid optics employing bothconventional and hybrid optics.

Turning now to FIGS. 9A and 9B, illustrated are views of an embodimentof hybrid optics employable with a guidance section of a weaponconstructed in accordance with the principles of the present invention.FIG. 9A illustrates an embodiment employing a clear front lens 905 withno optical properties other than being transparent at the opticalwavelength of interest. The focusing is accomplished by a FFL 910 asillustrated by rays 915, 920 where it can be seen that no focusing isaccomplished by the clear front lens. Contrast this with the embodimentillustrated in FIG. 9B where a front lens 925 of a target sensor of theguidance section, in concert with a FFL 930 focuses the incoming opticalsignals 935, 940 and, in so doing, generates a shorter focal lengthF_(L) than was generated in FIG. 9A for the same use of volume. Thefront lens 925 provides a cover to protect the target sensor fromenvironmental conditions and the FFL 930 behind the front lens 925cooperates with the front lens 925 to provide a multi-lens focusingsystem for the target sensor.

Therefore, by placing a small amount of optical focusing power in thefront lens 925, the focal length of the FFL 930 is allowed to be longer,making it easier to manufacture, while the optical system of FIG. 9B hasthe desirable property of a shorter focal length. Also, for clarity,note that the drawings of the FFL are not to scale. These lenses oftenare composed of hundreds of very small rings that are familiar andcommonly known to those skilled in the art. Thus, a hybrid system asdescribed herein employs less glass with additional favorable propertiesof less weight and optical loss. Finally, yet another embodiment is touse the back planar surface of the FFL 930 as a location for an opticalfilter 945 for filtering of unwanted wavelengths, for example most ofthe solar spectrum. An embodiment of the invention is an integral aftsection, tail fin, actuators, and prime power.

Turning now to FIG. 10, illustrated is a view of an embodiment of an aftsection constructed in accordance with the principles of the presentinvention. More specifically, FIG. 10 illustrates an aft section showingthe location of a battery and linear actuators 1005, and each singlepiece tail fin 1010 to which is attached an axel and linkage levelconnector. The power elements including batteries used in thisapplication comprehend military batteries, but also include commercialtypes. As an example, lithium batteries are both light and have aconsiderable shelf life.

Turning now to FIG. 11, illustrated is a view of an embodiment of an aftsection constructed in accordance with the principles of the presentinvention. More specifically, FIG. 11 demonstrates additional tail findetail. This innovative design is based on near zero hinge moments andcan use linkages and be subjected to forces consistent with radiocontrolled (“RC”) models. Note that the linear actuator fits directlyinto the tubular aft section 1105. In one embodiment, each of two pairsof tail fins 1110 operate in tandem while in an alternative embodiment,each fin is an independent moving surface. Under certain circumstances,of varying flight conditions, there are advantages to be gained inflight performance by changing the aspect ratio of the wings. Thiscapability is typically relegated to larger aircraft, but this inventioncomprehends an innovative implementation of providing variable aspectratio in a very limited space.

Turning now to FIGS. 12A and 12B, illustrated are views of an embodimentof a variable aspect wing ratio for the tail fins of an aft sectionconstructed in accordance with the principles of the present invention.In this embodiment, a rear fuselage 1205 and tail fins 1210 contain arod 1215 that moves in a direction, back and forth, along the centerlineof the rear fuselage. This causes links 1220 to force rods 1225 alongthe centerline of the tail fins 1210 in a direction that is normal torod 1215. In so doing, surface 1230 is retracted and extended asillustrated by extendable surface 1235. An end view (see FIG. 12B) ofthe tail fin 1210 along with the extendable surface 1235 is alsoillustrated. Therefore, with surface 1230 retracted, using formulasfamiliar to those skilled in the art, the aspect ratio A, defined as theratio of the span of the wings squared to the wing planform (e.g, shapeand layout of the tail fin) area is A=((2(B/2))̂2)/(B*C). With theextendable surface 1235 extended as shown, the aspect ratio becomesA=((2*((B/2+b)̂2)/(B*C+2*b*c), thus clearly showing a change in aspectratio. Thus, the tail fin 1210 has a modifiable control surface area,thereby changing an aspect ratio thereof. An alternative embodimentusing spring steel plates is also comprehended by this invention asdiscussed below.

Turning now to FIGS. 13A to 13F, illustrated are views of an embodimentof a variable aspect wing ratio for the tail fins of an aft sectionconstructed in accordance with the principles of the present invention.More specifically, FIG. 13A illustrates a planform view of a tail fin1305 with a cutout including a rod 1310 that moves in a manner similarto that illustrated in FIGS. 12A and 12B, except that in this embodimentthe variable surface is replaced by a deformable surface (e.g., springsteel sheet 1325) shown in the end view of FIG. 13B in an extendedstatus. The spring steel sheet 1325 is coupled to the rod 1310 via a pin1315 and dowel 1320 as illustrated in FIG. 13C, which provides a frontview without the tail fin. Thus, by moving the rod 1330, variable aspectratio is achieved again in a very confined space. As illustrated in FIG.13D, the spring steel sheet 1325 is partially retracted to modify thecontrol surface area of the tail fin (not shown in this FIGURE).Finally, FIG. 13E illustrates a planform view of the tail fin 1305having a cutout with the spring steel sheet 1325 retracted therebyfurther modifying the control surface area of the tail fin 1305 andchanging an aspect ratio thereof (see, also, FIG. 13F, which illustratesa front view with the tail fin removed). Thus, the tail fin 1305 has adeformable surface 1325 coupled to a rod 1310, pin 1315 and dowel 1320configured to extend or retract the deformable surface 1325 within orwithout the tail fin 1305.

Yet another embodiment of variable aspect ratio is also comprehended bythis invention wherein the tail fin dimensions may not change in flight.Referring now to FIGS. 14A to 14D, illustrated are views of anotherembodiment of a weapon including the tail fins of an aft section thereofconstructed in accordance with the principles of the present invention.FIG. 14A illustrates an end view of a present tail fin 1405. Forreliability and strength, it may be desirable to change its shape,however, in doing so, the aerodynamic characteristics of the tail fin1405 may also change dramatically. Therefore, FIG. 14B of the weapon1415 includes a variably shaped tail fin 1410 that does not vary theaerodynamic characteristics of the tail fin and therefore the weapon.This is because the body of the weapon 1415 as illustrated in FIG. 14Cis large with respect to the cylindrical area of the tail section 1420,thereby prohibiting much of the airflow around the tail fins at theirbase. The end view of FIG. 14D illustrates the shaped tail fin 1425 withcharacteristics of the flat fin outside the diameter of the weapon bodyand also showing additional mass and therefore strength in that area ofthe fin that is not active due to body shading.

Thus, in one embodiment, the weapon includes a warhead includingdestructive elements and a guidance section with a target sensorconfigured to guide the weapon to a target. The target sensor includes afront lens configured to provide a cover to protect the target sensorfrom an environment and a fast fresnel lens behind the front lens toprovide a multi-lens focusing system for the target sensor. In a relatedembodiment, the weapon includes an aft section including a tail finhaving a modifiable control surface area thereby changing an aspectratio thereof.

Additionally, a class of weapon systems, processes, and methods isdescribed with many features, including multiple modular guidancesystems, systems for decreasing the cost and time needed to load socalled weapons onto a delivery platform or vehicle such as an aircraft,and interfaces that support the same. The systems, processes, andmethods are also compatible with existing weapon envelopes of comparablesize, shape, weight, center of gravity, moment of inertia, andstructural strength. In so doing, the systems avoid lengthy andexpensive qualification for use with manned and unmanned deliveryplatforms such as ships, helicopters, self-propelled artillery and fixedwing aircraft, thus constituting systems and methods for introducingeffective new weapon system capabilities more quickly and at lessexpense. In addition, the systems increase the number of targets thatcan be attacked by a single delivery platform, whether manned orunmanned. The systems also simplify the integration of a weapon anddelivery platform.

As described herein, the weapon system provides an inductive circuit fortransfer of both power and data. For example, a number of projectilesuse inductive fuze setters to transfer data to the fuse of a shellbefore it is fired. Use of inductive principles for the transfer ofpower and data has a lengthy history.

U.S. Pat. No. 3,820,106 to Yamashita, et al. and U.S. Pat. No. 2,295,442to Wilhelm are examples of delivering both power and a signaling meansby a single connection, using inductive principles. Although Wilhelmdoes not cite specific references, he does make reference to the factthat delivering both power and signaling means over an alternatingcurrent circuit was familiar to those skilled in the art at the time.

Inductive electrical and electronic circuits are often used to powersignal transmitters because they are durable and offer predictableperformance in a variety of environments. Inductive electrical andelectronic circuits are used for long-term installations where a batterymay not be suitable. An inductive electronic circuit is used in avariety of applications to pass data, signals, and power back and forth,and may also be used in the antennae on both a signal transmitter and areceiver. An example of this application is used in some radio frequencyidentification (“RFID”) tags, where an inductive coupling in both anRFID tag and a reader use mutual inductance to power a microchip whichfunctions like an electronic transmitter, sending data to the readerantenna when the two are brought into close contact. On the otherextreme, inductive coupling is proposed as a means to deliver 50kilowatts for heavy material moving systems, and for electric trains.

Perhaps the most common uses are low power applications, providingbetween 0.5 watts (“W”) and 2 W for toothbrushes, electric shavers, andmobile telephones. More powerful systems are also common in the 2-5 Wrange and are sometimes used for small computers, personal digitalassistants, and multi-function mobile telephones. These consumer systemstypically require positioning accuracy of a few millimeters in order toalign the two coils.

Operating frequencies for these devices are commonly between 100kilohertz (“kHz”) and 1 megahertz (“MHz”), although examples outsidethis range are familiar to those skilled in the art. These consumerelectronics systems are used in conjunction with a wide range of batterytypes including nickel metal hydride (“NiMH”), lithium ion, and lithiumpolymer. In order to manage battery life and battery charging, some ofthese consumer electronics systems employ various means of adjusting thevoltage, current and power transferred.

In the case of U.S. Army artillery devices, a wide range of inductivedevices allow an artilleryman to set the fuze of a shell or a smartweapon. These devices vary widely in their performance, but it is wellknown to those familiar with the art that systems exist that transferapproximately 40 kilobits and provide adequate power for a 15 daybattery life and further provide confirmation of proper fuze set.

As an example, FIG. 15 illustrates a diagram of an exemplary inductivepower and data circuit. There are links with transferred power for shortdistances for implantable devices. Such links can provide tens of wattsof power, with an efficiency of more than 50 percent at useful coilfrequencies. Inductive data and power interfaces are used for a widerange of applications, and there are many examples of inductiveinterfaces both in industrial products, defense products, and researchand in clinical practice.

Weapon to delivery platform interfaces have been the subject ofextensive work since the invention of guided weapons in the 1940's. Inparticular, since the introduction of large numbers of tactical weaponswith guidance systems in the 1970's, this has been an area ofsignificant attention. The normal means of communicating with a weaponcarried on a delivery platform such as an aircraft is by means of anumbilical cable (as described in U.S. Pat. No. 6,615,116 to Ebert, etal.) and in some cases, by means of an arming wire or lanyard thatprovides a mechanical indication that a weapon or store has separatedfrom the aircraft. In some cases, the electrical signaling andmechanical indication are combined in a single assembly, as will befamiliar to those skilled in the art.

Interchangeability of weapon systems (e.g., guided bombs, rockets, andmissiles) is necessary for modern military aircraft. For example, anaircraft may use both air-to-air and air-to-surface weapon systems andmay perform both air engagement and ground support roles. However,various and generally unique inputs are required by each weapon type forstatus monitoring, targeting, arming, and ejecting the weapon system.

Military aircraft are designed to carry a plurality of weapon systems,some of which may not be of the same design. A central computer withinthe aircraft is responsive to pilot or aircrew commands and communicateswith each weapon system to monitor status, perform launch preparation,and execute launch commands. These weapon systems are coupled to atailored electronics or avionics system that responds to the aircraftcontroller. This avionics system serves as an interface between theaircraft controller and the weapon systems and is referred to here as aweapon interface system (“WIS”). The weapon interface system receivescommands from the aircraft controller and translates these commands toprovide mission information usable by one or more weapon systems.

The weapon interface system also receives power from the aircraft anddistributes this power to the weapon systems. In addition, the weaponinterface system controls and provides launch power to the weapon systemejectors that eject the weapon systems from the aircraft. The mechanicaland physical arrangements of carriage, including matters such asejection and sway bracing, are defined by MIL-STD-8591, which with itsrevisions and updates is incorporated herein by reference.

As noted, the aircraft may simultaneously carry a number of weaponsystems of differing designs, each weapon system design having its owninput requirements and providing its own outputs. In addition, theaircraft controller should be able to communicate with a selected weaponsystem, regardless of its design, independently of other weapon systems,so that, for example, the weapon system can provide status to theaircraft controller and the aircraft controller can specificallydesignate that weapon system for launch.

In the past, it has been necessary to extend cables from the aircraftcontroller to each weapon interface system and from the weapon interfacesystem to each weapon system to provide a direct and independentcommunication interface or link. This design has serious limitationsbecause it unnecessarily adds to the weight of the aircraft, and leadsto unnecessary power and cooling requirements, and electromagneticinterference. In response, MIL-STD-1553, entitled “MilitaryStandard—Aircraft Internal Time Division Command/Response Multiplex DataBus,” was introduced, which with its revisions and updates isincorporated herein by reference.

Turning now to FIG. 16, illustrated is a diagram of a representation ofthe MIL-STD-1553. MIL-STD-1553 replaced the multiple cable design with adual-redundant data bus design having only two shielded twisted paircables including a primary bus and a backup bus. The dual-redundant databus provides a common bus for connecting the aircraft controller to eachof the weapon carriage assemblies (each at its respective weaponinterface system). The weapon interface system of each weapon carriageassembly has a remote terminal for receiving signals from andtransmitting signals to the aircraft controller over the MIL-STD-1553bus. A central processing unit (“CPU”) processes these signals,selectively interacting with the various weapon carriage assemblycomponents, and responding to the aircraft controller; and a MIL-STD1553 bus controller controls transmissions between the centralprocessing unit and the weapon systems over MIL-STD 1553 weapon systembuses.

The weapon interface system/weapon system interface requirements for aweapon system capable of using a MIL-STD-1553 weapon interface systemare set forth in MIL-STD-1760, entitled “MilitaryStandard—Aircraft/Store Electric Interconnection System,” which with itsrevisions and updates is incorporated herein by reference. FIG. 17illustrates a diagram of exemplary interfaces controlled by aMIL-STD-1760, wherein ASI represents aircraft station interface, CSIrepresents carriage station interface, CSSI represents carriage storestation interface and MSI represents mission store interface. TheMIL-STD-1760 weapon systems include a MIL-STD-1553 remote interface.Electrical isolation is employed by the MIL-STD-1553 for coupled remoteterminals and bus controllers. Optical or inductive coupling devices forjoining two portions of dual-redundant data weapon system buses are usedto provide the isolation.

As conceptually illustrated in the block diagrams of FIGS. 18A and 18B,each MIL-STD-1760 compliant weapon is connected to the delivery orlaunch aircraft by means of an umbilical cable (sometimes referred to asa type one connector) or via a buffer (sometimes referred to as a typetwo connector) providing some combination of data interconnection,electrical power, logical signaling, and other connections. Since itsintroduction, weapons and launchers using MIL-STD-1760 have beenintegrated with delivery or launch platforms such as land vehicles andships. Therefore, the aircraft interfaces as used herein are exemplary,and are not intended to exclude any other type of platforms from whichweapons are released or launched.

The limitations of such connections have been a problem, in part due tothe need for loading crews to handle the connections, and to assure thatconnectors, wires and lanyards are properly installed, and in part dueto the potential for weapon failure when they do not disengage properly.Various means have been proposed to deal with the issue, such as the useof infrared systems (for example, see U.S. Pat. No. 5,681,008 toKinstler and U.S. Pat. No. 4,091,734 to Redmond, et al.).

Specific problems associated with the interconnection means in currentuse between delivery platforms, such as an aircraft or ship and weapons,include logistical problems caused by the fact that umbilicals, armingwires and lanyards are consumables, and the supply system may fail toprovide them in sufficient quantity, at the right time, and in thelocation where they are needed. In addition, the time required to makeand test these connections is often several minutes per weapon. As aresult, the critical time to reload an aircraft is extended. Anotherproblem with the present interconnection means is that of expense. Asguided weapons have become less expensive, the relative cost of theseconnections has increased.

Turning now to FIGS. 19 and 20, illustrated are diagrams of exemplarytriple ejector racks. FIG. 19 provides a front view of the tripleejector rack that can carry and eject three stores from a deliveryvehicle such as an aircraft. The arched structure at the top of theFIGURE is a suspension lug, which is the primary means of connecting therack to the aircraft. The angled pads are sway braces. One pair of thesway braces has an adapter, which allows safe carriage of stores thatwould otherwise be too small to be controlled by the sway braces. FIG.20 provides a side view of the triple ejector rack. From thisillustration, it can be seen that the sway braces can be adjusted toprovide positive contact with the store to be carried. The FIGURE alsoshows the flat spring adapter that fits onto the sway brace foot tocontrol stores that are too small for the sway brace to otherwisecontrol.

Thus, it would be beneficial to provide for a reusable interface,method, and system with the following attributes. The interface shouldbe capable of reuse, serving a plurality of weapon release events andsupporting connection of power and data without a direct optical orelectrical connection. The interface should be compatible with stringentelectromagnetic interference (“EMI”) environments and electromagneticcompatibility (“EMC”) requirements. The interface should be capable ofsupporting connections across a plurality of delivery platform types,and support interfaces when the crew actions involve the mechanicalloading of the weapon or store to the platform. The system should alsobe capable of providing a positive indication of weapon release andprovide both a primary and backup interface path.

The interface as described herein takes advantage of the fact that themechanical interface between a delivery platform such as an aircraft anda mission store, such as a weapon or pod, is very carefully controlled.Sway bracing or other means should be provided to restrain the storeagainst impact with the aircraft and against relative motion withrespect to the aircraft. The contact areas of the sway braces bearing onthe store are controlled so as to be sufficiently large in order toprevent damage to the store. Sway brace requirements are defined inMIL-STD-A-8591. Similarly, careful attention is paid to launch rails,clearance spacing, and other similar matters when rail launching methodsare employed. Thus, it is both common and practical to locate aninterface with precision and in such a manner as to be compatible withejection devices, fuze wires, sway braces, and other elements of theaircraft-store system.

In an exemplary embodiment, redundancy is used in the interface. Thismay be accomplished by means of redundant inductive coupling carrierfrequencies, use of both inductive and optical interfaces, by otherredundant means such as modulation schemes, and by other similarmethods. Redundancy may be desirable to improve reliability, to providefor an interface on the weapon that is compatible with a variety ofdelivery platforms, and to provide a means for power transmissionseparate from a means for data transmission. Other outcomes desirablefor system performance may also be achieved by redundancy, and this isnot an exhaustive list.

An important concern in the field of guided weapons is safety. Anexample of such a concern is the hazards of electromagnetic radiation toordnance (“HERO”). Simply stated, HERO considers how electromagneticenergy might cause an unintended explosive event. For the purposeshereof, HERO considerations are important. HERO considerations includedherein are band pass filters, which allow the inductive carrierfrequency, but exclude unwanted energy; a post-launch switch whichchanges the connection between the inductive pickup on the weapon andits internal components; and other electromagnetic interference andelectromagnetic compatibility design practices. Due to the proven safetyof inductive fuze setters, such safety matters in the context ofinductive interfaces are known to be practical by those skilled in theart.

Regarding the subject of post-launch switching, an exemplary embodimentuses a single assembly on the weapon for an inductive pickup, and for anantenna. Weapons often employ antennas for systems such as globalpositioning and data links. The options to change the characteristics ofthe coupling circuits greatly reduce the problems of such a sharedaperture. Such changes may be accomplished by a mechanical switch suchas the folding lug switch assembly, or by other means. On the launcherside of the interface, these same principles apply. In addition, aninterface foundation may include shielding to prevent the free spaceradiation of inductive energy or optical energy. Further, incorporationof the mandated MIL-SDT-1553 features, such as coupling transformers,provide additional HERO, electromagnetic interference, andelectromagnetic compatibility performance characteristics, in thosecases where an interface is based on the 1553 standard.

Turning now to FIG. 21, illustrated is a block diagram of an embodimentof a delivery platform (e.g., an aircraft) constructed according to theprinciples of the present invention. The aircraft includes a controller(e.g., a computer) 2110 responsive to pilot or aircrew commands andcommunicates with each weapon system to monitor status, perform launchpreparation, and execute launch commands and mission information. Theaircraft also includes sensors 2120 that assist a weapon to detect atarget in accordance with, for instance, global positioning, inertialsensing, pre-programmed knowledge-based data sets, target information,weapon information, warhead characteristics, safe and arm events, fuzinglogic and environmental information. The aircraft also includesauxiliary systems 2130 to provide auxiliary functions for the aircraft.The aircraft also includes a power system 2140 configured to provide ACand DC power to systems therefor. The aircraft also includes a weaponswitching system 2150 configured to provide switching and discretesignals for the weapon systems. The aircraft also includes anaircraft/weapon electrical interconnection system 2160 compatible, forinstance, with MIL-STD 1760, configured to provide an electricalinterface to a rack system 2170 for the weapon system. The aircraft alsoincludes a weapon interface system 2180 including a translationinterface 2190 and a weapon coupler (e.g., an inductive or opticalcoupler) 2200. The translation interface 2190 provides an interfacebetween the aircraft/weapon electrical interconnection system 2160 andan inductive power and data circuit therein. The weapon coupler 2200provides an interface to the weapon system to provide real-time missioninformation thereto.

Turning now to FIG. 22, illustrated is a view of an embodiment of a racksystem and portions of a weapon interface system constructed accordingto the principles of the present invention. More particularly, FIG. 22illustrates a side view of a triple ejector rack that ejects weaponsfrom a delivery platform such as an aircraft. A weapon coupler (e.g., aninductive coupler) 2250 of the weapon interface system is formed from aflexible material being substantially planar, such as polycarbonate,formed into a flat spring adapter that fits onto the familiar adapter,which in turn connects to sway brace foot 2260. Thus, it positions aninterface, providing location control, a paramagnetic structure, andstill provides a means to control stores that are too small for the swaybrace 2270 to otherwise control.

Turning now to FIG. 23, illustrated is a diagram of an embodiment of aweapon coupler (e.g., an inductive coupler) 2310 constructed accordingto the principles of the present invention. The inductive coupler 2310is formed from a flexible material, such as polycarbonate formed intoflat spring adapter which fits onto the familiar adapter. Note thatthere are two positions A and B, which do not require a penetration ofthe current adapter 2320. Penetration of the current spring adaptor 2320has advantages in some exemplary embodiments, but is not necessary, asshown here.

Turning now to FIG. 24, illustrated is a view of an embodiment of a racksystem (e.g., a triple ejector rack) 2410 and portions of a weaponinterface system constructed according to the principles of the presentinvention. A canister, or launch tube 2420 of the weapon system issuspended from the triple ejector rack 2410. The canister 2420 containsone or more weapons or munitions 2430 to be delivered. A weapon coupler(e.g., an inductive or optical coupler) is constructed to provide ameans of data and/or power transfer as previously described. Thisextends the previous weapon coupler to an entire canister 2420, insteadof an arced plate as shown in the previous FIGURE. An interface coil ofthe weapon coupler may extend coaxially about the canister so as toallow weapon system loading independent of rotational orientation.

Turning now to FIGS. 25 to 28B, illustrated are cross sectional views ofembodiments of weapon couplers constructed according to the principlesof the present invention. Beginning with FIG. 25, the weapon coupler(e.g., inductive coupler) includes a weapon interface (e.g., a Tefloninterface to a weapon) 2510, an inductive coil (e.g., Mylar withinductive coil printed thereon) 2520, a spacer (e.g., a Teflon spacer)2530, a shield (e.g., a magnetic shielding material such as Metglasmagnetic alloy 2705M) 2540, and a protection layer (e.g., a Teflonabrasion protection layer) 2550.

Regarding FIG. 26, the weapon coupler (e.g., inductive coupler) includesa weapon interface (e.g., a Teflon interface to a weapon) 2610, aninductive coil (e.g., Mylar with inductive coil printed thereon) 2620, aspacer (e.g., a Teflon spacer) 2630, and a spring steel layer (e.g., aTeflon abrasion protection layer) 2640. Regarding FIG. 27, the weaponcoupler (e.g., inductive coupler) includes a weapon interface (e.g., aTeflon interface to a weapon) 2710, an inductive coil (e.g., Mylar withinductive coil printed thereon) 2720, a spacer (e.g., a Teflon spacer)2730, a shield (e.g., a magnetic shielding material such as Metglasmagnetic alloy 2705M) 2740, and a protection layer (e.g., a Teflonabrasion protection layer) 2750.

Regarding FIGS. 28A and 28B, illustrated are side and cross sectionalviews of an embodiment of a weapon coupler (e.g., inductive coupler)constructed according to the principles of the present invention. Theweapon coupler includes a weapon interface (e.g., a Teflon interface toa weapon) 2810, an inductive coil (e.g., Mylar with inductive coilprinted thereon) 2820, a primary structure (e.g., a Kevlar composite,PVC) 2830, a shield (e.g., a magnetic shielding material such as Metglasmagnetic alloy 2705M) 2840, and a protection layer (e.g., a Teflonabrasion protection layer) 2850.

Additionally, exemplary embodiments of the present invention have beenillustrated with reference to specific components. Those skilled in theart are aware, however, that components may be substituted (notnecessarily with components of the same type) to create desiredconditions or accomplish desired results. For instance, multiplecomponents may be substituted for a single component and vice-versa. Theprinciples of the present invention may be applied to a wide variety ofweapon systems. Those skilled in the art will recognize that otherembodiments of the invention can be incorporated into a deliveryplatform including a weapon interface system. Absence of a discussion ofspecific applications employing principles of a delivery platform andweapon interface system does not preclude that application from fallingwithin the broad scope of the present invention.

Although the present invention has been described in detail, thoseskilled in the art should understand that they can make various changes,substitutions and alterations herein without departing from the spiritand scope of the invention in its broadest form. Moreover, the scope ofthe present application is not intended to be limited to the particularembodiments of the process, machine, manufacture, composition of matter,means, methods and steps described in the specification. As one ofordinary skill in the art will readily appreciate from the disclosure ofthe present invention, processes, machines, manufacture, compositions ofmatter, means, methods, or steps, presently existing or later to bedeveloped, that perform substantially the same function or achievesubstantially the same result as the corresponding embodiments describedherein may be utilized according to the present invention. Accordingly,the appended claims are intended to include within their scope suchprocesses, machines, manufacture, compositions of matter, means,methods, or steps.

What is claimed is:
 1. A weapon system, comprising: a rack systemcoupled to an electrical interconnection system of a delivery platformand including an adapter; and a weapon interface system, coupled to saidadapter and extending along a cannister, configured to provide power anddata from said electrical interconnection system to said cannister viaan inductive coupler of said weapon interface system.
 2. The weaponsystem as recited in claim 1 wherein said weapon interface system isconfigured to deliver said power and said data from said electricalinterconnection system to a weapon within and via said cannister.
 3. Theweapon system as recited in claim 1 wherein said weapon interface systemis configured to deliver said power and said data from said electricalinterconnection system to a plurality of weapons within and via saidcannister.
 4. The weapon system as recited in claim 1 wherein saidweapon interface system extends coaxially about said canister.
 5. Theweapon system as recited in claim 1 wherein said weapon interface systemis formed from a flexible and substantially planar material and locatedwithin said adapter of said rack system.
 6. The weapon system as recitedin claim 1 wherein said weapon interface system comprises a weaponinterface, an inductive coil, a shield, and a protection layer.
 7. Theweapon system as recited in claim 1 wherein said weapon interface systemcomprises a weapon interface, an inductive coil, a spacer, and a springsteel layer.
 8. The weapon system as recited in claim 1 wherein saidweapon interface system comprises a weapon interface, an inductive coil,a primary structure, a shield, and a protection layer.
 9. The weaponsystem as recited in claim 1 wherein said weapon interface system isformed from a polycarbonate material.
 10. The weapon system as recitedin claim 1 wherein said data comprises mission information.
 11. A methodof operating a weapon system, comprising: providing a rack systemcoupled to an electrical interconnection system of a delivery platformand including an adapter; and delivering power and data from saidelectrical interconnection system to a cannister via an inductivecoupler of a weapon interface system coupled to said adapter andextending along said cannister.
 12. The method as recited in claim 11wherein said delivering comprises delivering said power and said datafrom said electrical interconnection system to a weapon within and viasaid cannister.
 13. The method as recited in claim 11 wherein saiddelivering comprises delivering said power and said data from saidelectrical interconnection system to a plurality of weapons within andvia said cannister.
 14. The method as recited in claim 11 wherein saidweapon interface system extends coaxially about said canister.
 15. Themethod as recited in claim 11 wherein said weapon interface system isformed from a flexible and substantially planar material and locatedwithin said adapter of said rack system.
 16. The method as recited inclaim 11 wherein said weapon interface system comprises a weaponinterface, an inductive coil, a shield, and a protection layer.
 17. Themethod as recited in claim 11 wherein said weapon interface systemcomprises a weapon interface, an inductive coil, a spacer, and a springsteel layer.
 18. The method as recited in claim 11 wherein said weaponinterface system comprises a weapon interface, an inductive coil, aprimary structure, a shield, and a protection layer.
 19. The method asrecited in claim 11 wherein said weapon interface system is formed froma polycarbonate material.
 20. The method as recited in claim 11 whereinsaid data comprises mission information.